A solar wing drive rotation mechanism and its thermal design method and thermal control method

Abstract

The present invention discloses a solar wing drive rotary mechanism and its thermal design method and thermal control method, which belong to the technical field of communication satellites. The solar wing drive rotary mechanism includes an A-axis and a cabin. The A-axis includes a slip ring, a motor and a bracket. The motor is coaxially arranged at the first end of the slip ring, and the output end of the motor is transmission-connected to the slip ring; the bracket includes a bottom plate extending along the axial direction of the slip ring, and an end plate flange is respectively arranged at both ends of the bottom plate. The motor is heat-conductingly mounted on one end plate flange through a first flange, and the second end of the slip ring is heat-conductingly mounted on another end plate flange through a second flange. A plurality of heaters are spaced apart on the bottom plate along the extension direction of the bottom plate, and the bottom plate is heat-conductingly connected to the cabin. The present invention enables the solar wing drive mechanism to have a good heat dissipation effect.

Description

Technical Field

[0001] The present invention relates to the technical field of communication satellites, and in particular to a solar wing drive rotation mechanism and a thermal design method and a thermal control method thereof. Background Art

[0002] In the field of communication satellites, SADA (Solar Array Drive Assembly) with two-axis control capabilities is generally selected to ensure that the solar panels continue to point to the sun and ensure the stability of satellite energy.

[0003] SADA includes A-axis and B-axis. A-axis is a rotary mechanism installed in the cabin, and B-axis is installed outside the cabin. Both axes are powered on for a long time on the track, resulting in high heat consumption. In the prior art, heat is only dissipated by spraying white paint on the outer surface of the cabin, but the heat dissipation effect is poor. Summary of the invention

[0004] The object of the present invention is to provide a solar wing drive rotating mechanism and its thermal design method and thermal control method, so as to solve the technical problem of poor heat dissipation effect of the solar wing drive mechanism existing in the prior art.

[0005] As conceived above, the technical solution adopted by the present invention is:

[0006] A solar wing driven rotary mechanism, comprising an A-axis, the solar wing driven rotary mechanism also comprising a cabin, the A-axis comprising:

[0007] Slip rings;

[0008] A motor is coaxially arranged at the first end of the slip ring, and an output end of the motor is transmission-connected to the slip ring;

[0009] The bracket comprises a base plate extending along the axial direction of the slip ring, an end plate flange is respectively arranged at both ends of the base plate, the motor is thermally mounted on one of the end plate flanges through a first flange, the second end of the slip ring is thermally mounted on the other end plate flange through a second flange, a plurality of heaters are spaced apart on the base plate along the extension direction of the base plate, and the base plate is thermally connected to the cabin body.

[0010] Optionally, reinforced side plates are provided on both sides of the bottom plate, the side portion of each reinforced side plate is connected to the bottom plate, and the two ends of each reinforced side plate are respectively connected to the two end plate flanges.

[0011] Optionally, weight-reducing holes are provided on the reinforced side panels.

[0012] Optionally, the cabin body includes a first cabin plate, a second cabin plate, a third cabin plate and a fourth cabin plate connected end to end in sequence, the bottom plate is connected to the first cabin plate, and the two end plate flanges of the bracket are respectively connected to the second cabin plate and the fourth cabin plate.

[0013] Optionally, the second deck is connected to one of the end plate flanges via a first rotary shaft, a first hole for mounting the first rotary shaft is provided on the second deck, and the solar wing driving rotary mechanism further comprises a first hole-blocking heat-insulating member, wherein the first hole-blocking heat-insulating member comprises:

[0014] An inner support frame, one end of which is connected to the end plate flange, and the other end of which is connected to the second cabin plate around the circumference of the first hole, and the first rotary axis is located in the inner support frame;

[0015] The multi-layer heat-insulating assembly is wrapped around the outer side of the inner supporting frame and encloses to form a first heat-insulating space.

[0016] Optionally, a heat-conductive insulating film is provided between the bottom plate and the first cabin plate.

[0017] A thermal design method for a solar wing driven rotary mechanism is provided, wherein the thermal design is performed on the above-mentioned solar wing driven rotary mechanism, comprising:

[0018] Spray black paint on the exposed surfaces of the slip ring, motor, first flange and second flange;

[0019] Filling thermal conductive silicone grease in the gap between the motor and the first flange;

[0020] Spray white paint on the end plate flanges and anodize the bottom plate surface black;

[0021] Installing the bottom plate and the cabin body with heat conduction insulation;

[0022] Installing the heater on the surface of the base plate facing the slip ring according to a preset position;

[0023] A first temperature sensor is arranged on the surface of the slip ring, and a second temperature sensor is arranged on the surface of the motor.

[0024] Optionally, the cabin body comprises a first cabin plate, a second cabin plate, a third cabin plate and a fourth cabin plate connected end to end in sequence, the bottom plate is connected to the first cabin plate, and the two end plate flanges of the bracket are connected to the second cabin plate and the fourth cabin plate respectively;

[0025] The second deck is connected to one of the end plate flanges via a first rotary shaft, a first hole for installing the first rotary shaft is provided on the second deck, and the solar wing driving rotary mechanism further comprises a first hole blocking heat insulating member;

[0026] The thermal design method of the solar wing drive rotary mechanism also includes:

[0027] Spray white paint on the outer surface of the first deck and spray black paint on the inner surface;

[0028] The first hole-sealing heat-insulating component is installed to seal the first hole.

[0029] A method for thermal control of a solar wing driven rotary mechanism, for thermally controlling the above-mentioned solar wing driven rotary mechanism, comprises the following steps:

[0030] S01. A plurality of temperature control points are arranged on the bottom plate, each heater corresponds to one temperature control point, and the current temperature of each temperature control point is monitored in real time;

[0031] S02, determining whether the temperature of each temperature control point is within a set range, if the temperature of each temperature control point is within the set range, executing step S03; otherwise, executing step S04;

[0032] S03, determining whether the difference between the maximum and minimum current temperatures of the plurality of temperature control points is greater than a set difference; if so, controlling the power of the heater corresponding to the temperature control point with the lowest current temperature to increase by a first set value for a first set time, and returning to execute step S01; if not, no operation;

[0033] S04, adjusting the heating power of the heater corresponding to the temperature control point whose temperature is not within the set range, and continuing for a second set time, returning to execute step S01, wherein the second set time is greater than the first set time.

[0034] Optionally, the step S04 includes:

[0035] S041, determining whether the current temperature of the temperature control point whose temperature is not within the set range is greater than the minimum value of the set range, if not, controlling the power of the heater corresponding to the temperature control point whose temperature is not within the set range to be increased by a second set value, and continuing for the second set time, returning to execute step S01, the second set value is greater than the first set value; if yes, executing step S042;

[0036] S042, controlling the power of the heater corresponding to the temperature control point whose temperature is not within the set range to be reduced by the second set value, and continuing for the second set time, and then returning to execute step S01.

[0037] In the solar wing driven rotary mechanism proposed by the present invention, the heat of the slip ring and the heat of the motor are respectively conducted to the bracket through the second flange and the first flange, and the bracket then transfers the heat to the cabin through the bottom plate, and the cabin conducts the heat to the external space of the cabin, so that the heat dissipation performance of the solar wing driven rotary mechanism is good at high temperature. At the same time, a plurality of heaters are arranged at intervals on the bottom plate, and by controlling the heating temperature of the heaters, the solar wing driven rotary mechanism can be actively temperature controlled, and the temperature of the A axis is ensured to be within the normal working temperature range in a low temperature environment.

[0038] The thermal design method of the solar wing drive rotary mechanism proposed in the present invention can ensure normal heat dissipation of the A-axis when the temperature is too high, and can achieve autonomous temperature control at low temperatures to ensure that the temperature of the A-axis is within the normal operating temperature range.

[0039] The thermal control method of the solar wing driven rotary mechanism proposed in the present invention has a good heat dissipation effect of the solar wing driven rotary mechanism. The thermal control method can ensure that the temperature of the A axis is within the normal operating temperature range under low temperature conditions, and can reduce the temperature difference between the two ends of the bracket, thereby ensuring the temperature control accuracy of the SADA-A axis. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0041] Figure 1 is a schematic structural diagram of the A-axis provided in the first embodiment of the present invention;

[0042] Figure 2 This is a schematic diagram of the A-axis provided in the first embodiment of the present invention being installed on the cabin and the frame being installed;

[0043] Figure 3 It is a schematic diagram of the A-axis provided in the first embodiment of the present invention being installed on the cabin body and the first hole blocking heat insulation component being installed;

[0044] Figure 4 yes Figure 3 Schematic diagram after the multi-layer insulation components are hidden.

[0045] In the figure:

[0046] 1. A-axis; 11. Slip ring; 12. Motor; 13. Bracket; 131. Bottom plate; 132. End plate flange; 133. Strengthening side plate; 14. First flange; 15. Second flange; 16. Heater;

[0047] 2. Cabin; 21. First cabin board; 22. Second cabin board; 221. First opening; 23. Third cabin board; 24. Fourth cabin board;

[0048] 3. The first rotary axis;

[0049] 4. First opening sealing insulation component; 41. Multi-layer insulation assembly; 421. Frame. DETAILED DESCRIPTION

[0050] In order to make the technical problems solved by the present invention, the technical solutions adopted and the technical effects achieved clearer, the technical solutions of the present invention are further described below in conjunction with the accompanying drawings and through specific implementation methods. It is understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for the convenience of description, only the parts related to the present invention are shown in the accompanying drawings, not all.

[0051] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions.

[0052] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] Embodiment 1

[0054] See also Figure 1-Figure 4 This embodiment provides a solar wing drive rotation mechanism, which has good heat dissipation performance and can ensure normal heat dissipation of the A-axis 1 when the temperature is too high. At low temperatures, it can achieve autonomous temperature control to ensure that the temperature of the A-axis 1 is within the normal operating temperature range.

[0055] Specifically, in this embodiment, the solar wing driving rotation mechanism includes an A-axis 1 and a cabin body 2 , and the A-axis 1 includes a slip ring 11 , a motor 12 and a bracket 13 .

[0056] The motor 12 is coaxially disposed at a first end of the slip ring 11 , and an output end of the motor 12 is transmission-connected to the slip ring 11 .

[0057] The bracket 13 includes a base plate 131 extending along the axial direction of the slip ring 11, and an end plate flange 132 is respectively provided at both ends of the base plate 131. The motor 12 is thermally mounted on one end plate flange 132 through a first flange 14, and the second end of the slip ring 11 is thermally mounted on the other end plate flange 132 through a second flange 15. A plurality of heaters 16 are spaced apart on the base plate 131 along the extension direction of the base plate 131, and the base plate 131 is thermally insulatedly connected to the cabin 2.

[0058] In the solar wing driven rotary mechanism provided in this embodiment, the heat of the slip ring 11 and the heat of the motor 12 are respectively conducted to the bracket 13 through the second flange 15 and the first flange 14, and the bracket 13 then transfers the heat to the cabin 2 through the bottom plate 131, and the cabin 2 conducts the heat to the external space of the cabin 2, so that the heat dissipation performance of the solar wing driven rotary mechanism is good at high temperature. At the same time, a plurality of heaters 16 are arranged at intervals on the bottom plate 131, and by controlling the heating temperature of the heaters 16, the solar wing driven rotary mechanism can be actively temperature controlled, and the temperature of the A axis 1 is ensured to be within the normal operating temperature range in a low temperature environment.

[0059] Specifically, the heater 16 is a thin film heater, which is installed on the base plate 131 by bonding. The temperature control threshold of the heater 16 is [-10,5], and the temperature control power is 6W. By controlling the heating of the heater 16, on the one hand, it ensures that the temperature of the A-axis 1 is within the normal operating temperature range under low temperature conditions. On the other hand, it can reduce the temperature difference at both ends of the bracket 13 to ensure the temperature control accuracy of the A-axis 1 of SADA.

[0060] Furthermore, in this embodiment, reinforcing side plates 133 are provided on both sides of the bottom plate 131, the side of each reinforcing side plate 133 is connected to the bottom plate 131, and the two ends of each reinforcing side plate 133 are respectively connected to the two end plate flanges 132. By providing the reinforcing side plates 133, the structural strength of the bracket 13 is ensured.

[0061] Preferably, weight-reducing holes are provided on the reinforcing side plate 133 to achieve a lightweight design of the bracket 13 .

[0062] Specifically, in this embodiment, the cabin 2 includes a first cabin plate 21, a second cabin plate 22, a third cabin plate 23 and a fourth cabin plate 24 which are connected end to end in sequence, the bottom plate 131 is connected to the first cabin plate 21, and the two end plate flanges 132 of the bracket 13 are respectively connected to the second cabin plate 22 and the fourth cabin plate 24, thereby realizing the installation of the bracket 13 in the cabin 2.

[0063] Preferably, a thermally conductive insulating film is provided between the bottom plate 131 and the first cabin plate 21, and they are connected by a connector. Specifically, the thermally conductive insulating film includes an insulating film, and both sides of the insulating film are provided with a thermally conductive silicone grease layer. Specifically, the insulating film is a 25 um thick polyimide film, and thermally conductive silicone grease is coated on both sides of the insulating film to form a thermally conductive silicone grease layer.

[0064] The bottom plate 131 is connected to the first deck plate 21, so that the first deck plate 21 becomes a heat dissipation surface, and utilizes the thermal coupling between the structures to dissipate the heat of the solar wing driving rotary mechanism to the cold space.

[0065] Furthermore, the solar wing drive rotating mechanism is a "through-type" solar wing drive rotating mechanism.

[0066] The second cabin plate 22 is connected to an end plate flange 132 via a first rotating shaft 3. A first hole 221 for installing the first rotating shaft 3 is opened on the second cabin plate 22. The solar wing driving rotating mechanism also includes a first hole blocking thermal insulation component 4. The first hole blocking thermal insulation component 4 includes an internal support frame and a multi-layer thermal insulation component 41.

[0067] One end of the inner support frame is connected to the end plate flange 132, and the other end is connected to the second cabin plate 22 around the circumference of the first opening 221. The first rotary shaft 3 is located inside the inner support frame. The multi-layer insulation assembly 41 is wrapped around the outer side of the inner support frame and encloses to form a first insulation space.

[0068] By providing the first hole blocking heat insulating member 4 , it is possible to prevent external heat flow from entering the cabin through the first hole 221 and affecting the temperature of the A-axis 1 .

[0069] Specifically, in this embodiment, the internal support frame includes multiple skeletons 421, one end of each skeleton 421 is fixedly connected to the end plate flange 132 by Velcro, and silicone rubber and double-sided tape are used for auxiliary fixation; the other end is fixedly connected to the second cabin plate 22 by pins, and silicone rubber and double-sided tape are used for auxiliary fixation.

[0070] Preferably, the multiple skeletons 421 roughly envelop a conical surface. Specifically, the skeleton 421 is made of a 100 μm polyimide film.

[0071] Specifically, the multi-layer heat insulation assembly 41 includes a five-unit multi-layer heat insulation material and a multi-layer mask wrapped around the five-unit multi-layer heat insulation material. The five-unit multi-layer heat insulation material is composed of 6 layers of double-sided aluminized polyester film (white film) and 5 layers of polyester mesh, of which the outermost layers on both sides are thickened (the outermost layer is 18mm to 20mm thick, and the middle layer is 6.3mm thick) double-sided aluminized polyester film; the multi-layer mask is a single-sided aluminized polyimide film (yellow film), which wraps the five-unit multi-layer heat insulation material inside, and the edges should be tightly wrapped. The flanges of the multi-layer mask are fixed with single-sided aluminized pressure-sensitive tape at a spacing of about 50mm.

[0072] The five-unit multi-layer thermal insulation material is wrapped on the inner support frame, and the multi-layer membrane wraps the five-unit multi-layer thermal insulation material inside.

[0073] Specifically, when designing the first hole blocking insulation 4, the overall size and installation position of the inner support frame and the multi-layer insulation assembly 41, it is necessary to consider the shrinkage margin of the inner support frame and the multi-layer insulation assembly 41 when exposed to cold, to ensure that both can remain fluffy in a low temperature environment and will not generate shrinkage tension on the fixed structure.

[0074] Furthermore, the fourth cabin plate 24 is connected to another end plate flange 132 via a second rotating shaft. A second hole for installing the second rotating shaft is opened on the fourth cabin plate 24. The solar wing driving rotating mechanism also includes a second hole blocking insulation component. The structure of the second hole blocking insulation component is the same as that of the first hole blocking insulation component 4, and also includes an internal support frame and a multi-layer insulation assembly 41.

[0075] One end of the inner support frame of the second hole-blocking heat-insulating member is connected to the end plate flange 132, and the other end is connected to the fourth cabin plate 24 around the circumference of the second hole, and the second rotary axis is located in the inner support frame. The multi-layer heat insulation assembly 41 of the second hole-blocking heat-insulating member is wrapped around the outer side of the inner support frame and enclosed to form a second heat insulation space.

[0076] By providing the first hole blocking heat insulating member 4 and the second hole blocking heat insulating member, the first hole 221 and the second hole are blocked, thereby reducing the influence of the external heat flow on the A axis 1.

[0077] Embodiment 2

[0078] This embodiment provides a thermal design method for a solar wing driven rotary mechanism, and performs thermal design on the solar wing driven rotary mechanism in Embodiment 1. The thermal design method for the solar wing driven rotary mechanism can ensure normal heat dissipation of the A axis 1 when the temperature is too high, and can achieve autonomous temperature control at low temperatures to ensure that the temperature of the A axis 1 is within the normal operating temperature range.

[0079] Thermal design methods for solar wing drive slewing mechanisms include:

[0080] S1. Spray black paint on the exposed surfaces of the slip ring 11, the motor 12, the first flange 14 and the second flange 15. Specifically, all surfaces of the first flange 14 and the second flange 15 except the mounting surface are sprayed with black paint. Optionally, the black paint is E51-M black paint with an emissivity greater than 0.85.

[0081] S2. Fill the gap between the motor 12 and the first flange 14 with thermal grease.

[0082] S3. Spray white paint on the end plate flange 132 and perform black anodizing on the surface of the base plate 131; specifically, the material of the bracket 13 is 6 series aluminum alloy material with a thermal conductivity of 201W / m / K; spray SR107-ZK white paint on the end plate flange 132, and the designed initial absorption rate of SR107-ZK white paint is 0.18 and the emissivity is 0.87; except for the end plate flange 132, the other surfaces of the bracket 13 are all subjected to black anodizing, and the emissivity is greater than 0.85.

[0083] S4. Install the bottom plate 131 and the cabin body 2 in a heat-conducting and insulating manner; specifically, there is an insulating film between the bottom plate 131 and the cabin body 2, and thermal grease is coated on both sides of the insulating film to form a thermal grease layer; optionally, the insulating film is a 25um thick polyimide film.

[0084] S5. Paste and install the heater 16 to the surface of the base plate 131 facing the slip ring 11 according to the preset position; set a first temperature sensor on the surface of the slip ring 11 and set a second temperature sensor on the surface of the motor 12 to better monitor the temperature of the A-axis 1.

[0085] S6. Spray white paint on the outer surface of the first cabin plate 21 and spray black paint on the inner surface; specifically, spray SR107-ZK white paint on the outer surface of the first cabin plate 21 to serve as a heat dissipation surface to dissipate the heat of the A-axis 1 to the cold space through the heat dissipation surface; spray E51-M black paint on the inner surface of the first cabin plate 21 to enhance the radiation heat exchange between the A-axis 1 and the first cabin plate 21.

[0086] S7, installing the first hole blocking heat insulating member 4 to block the first hole 221.

[0087] By adopting the above-mentioned thermal design method, the temperature of the A-axis 1 can be controlled within the range of -10°C to +30°C, which meets the normal operating temperature range of the SADA-A axis and has a margin of more than 10°C, thereby improving the reliability of the SADA-A axis operation and realizing the long-term stable operation of the SADA-A axis on track.

[0088] Embodiment 3

[0089] This embodiment provides a thermal control method for a solar wing driven rotary mechanism, which can ensure that the temperature of the A-axis 1 is within the normal operating temperature range under low temperature conditions, and can reduce the temperature difference at both ends of the bracket 13, thereby ensuring the temperature control accuracy of the A-axis 1 of the SADA.

[0090] Specifically, the thermal control method of the solar wing driven rotary mechanism is used to perform thermal control on the solar wing driven rotary mechanism in the first embodiment, and includes the following steps:

[0091] S01. A plurality of temperature control points are arranged on the bottom plate 131. Each heater 16 corresponds to one temperature control point. The current temperature of each temperature control point is monitored in real time.

[0092] S02, judging whether the temperature of each temperature control point is within the set range, if the temperature of each temperature control point is within the set range, executing step S03; otherwise, executing step S04.

[0093] S03, determine whether the difference between the maximum and minimum values ​​of the current temperatures of several temperature control points is greater than the set difference. If so, control the power of the heater 16 corresponding to the temperature control point with the lowest current temperature to increase by the first set value, and continue for the first set time, and then return to step S01; if not, no operation. If the temperatures of multiple temperature control points are within the set range, it means that the temperature of the A axis 1 is relatively uniform at this time. By executing step S03, the temperature of the A axis 1 can be adjusted to be more uniform.

[0094] S04, adjusting the heating power of the heater 16 corresponding to the temperature control point whose temperature is not within the set range, and continuing for a second set time, returning to step S01, the second set time being greater than the first set time. If the temperature of at least one of the multiple temperature control points is not within the set range, it means that the temperature of the A-axis 1 is relatively uneven at this time, and the temperature of the A-axis 1 needs to be adjusted to a relatively uniform state first; since the temperature of the A-axis 1 is relatively uneven at this time, the second set time is greater than the first set time.

[0095] Further, step S04 includes:

[0096] S041. Determine whether the current temperature of the temperature control point whose temperature is not within the set range is greater than the minimum value of the set range. If not, control the power of the heater 16 corresponding to the temperature control point whose temperature is not within the set range to be increased by a second set value. After the second set time is continued, return to execute step S01. The second set value is greater than the first set value. If so, execute step S042.

[0097] S042, controlling the power of the heater 16 corresponding to the temperature control point whose temperature is not within the set range to be reduced by a second set value, and continuing for a second set time, and then returning to step S01.

[0098] The above embodiments are only to illustrate the basic principles and characteristics of the present invention. The present invention is not limited by the above embodiments. Without departing from the spirit and scope of the present invention, the present invention may be subject to various changes and modifications, which are within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A solar wing drive rotary mechanism, comprising an A-axis (1), characterized in that: The solar wing driving rotary mechanism further comprises a cabin (2), and the A axis (1) comprises: Slip ring (11); A motor (12) is coaxially arranged at a first end of the slip ring (11), and an output end of the motor (12) is drivingly connected to the slip ring (11); The bracket (13) comprises a bottom plate (131) extending along the axial direction of the slip ring (11), an end plate flange (132) is provided at each end of the bottom plate (131), the motor (12) is heat-conductingly mounted on one of the end plate flanges (132) via a first flange (14), the second end of the slip ring (11) is heat-conductingly mounted on the other end plate flange (132) via a second flange (15), a plurality of heaters (16) are spaced apart on the bottom plate (131) along the extension direction of the bottom plate (131), and the bottom plate (131) is heat-conductingly connected to the cabin (2); The cabin body (2) comprises a first cabin plate (21), a second cabin plate (22), a third cabin plate (23) and a fourth cabin plate (24) which are connected end to end in sequence, the bottom plate (131) is connected to the first cabin plate (21), and the two end plate flanges (132) of the bracket (13) are respectively connected to the second cabin plate (22) and the fourth cabin plate (24); The second cabin plate (22) is connected to one of the end plate flanges (132) via a first rotating shaft (3); the second cabin plate (22) is provided with a first hole (221) for mounting the first rotating shaft (3); the solar wing driving rotating mechanism further comprises a first hole-blocking heat insulating member (4); the first hole-blocking heat insulating member (4) comprises: an inner support frame, one end of which is connected to the end plate flange (132), and the other end of which is connected to the second cabin plate (22) around the circumference of the first hole (221), and the first rotary shaft (3) is located inside the inner support frame; A multi-layer heat insulation component (41) is wrapped around the outer side of the inner support frame and encloses a first heat insulation space.

2. The solar wing drive rotary mechanism according to claim 1, characterized in that: Reinforced side plates (133) are provided on both sides of the bottom plate (131), the side of each reinforced side plate (133) is connected to the bottom plate (131), and the two ends of each reinforced side plate (133) are respectively connected to the two end plate flanges (132).

3. The solar wing drive rotary mechanism according to claim 2, characterized in that: The reinforced side plate (133) is provided with a weight-reducing hole.

4. The solar wing drive rotary mechanism according to claim 1, characterized in that: A heat-conductive insulating film is provided between the bottom plate (131) and the first cabin plate (21).

5. A thermal design method for a solar wing drive rotary mechanism, characterized in that: The thermal design of the solar wing drive rotary mechanism according to any one of claims 1 to 4 comprises: Spraying black paint on the exposed surfaces of the slip ring (11), the motor (12), the first flange (14) and the second flange (15); Filling a gap between the motor (12) and the first flange (14) with thermally conductive silicone grease; Spray white paint on the end plate flange (132) and perform black anodizing on the surface of the bottom plate (131); Installing the bottom plate (131) and the cabin body (2) in a heat-conducting and insulating manner; Installing the heater (16) at a preset position on the surface of the bottom plate (131) facing the slip ring (11); A first temperature sensor is arranged on the surface of the slip ring (11), and a second temperature sensor is arranged on the surface of the motor (12); Spraying white paint on the outer surface of the first cabin plate (21) and spraying black paint on the inner surface; The first hole-sealing heat-insulating component (4) is installed to seal the first hole (221).

6. A thermal control method for a solar wing drive rotary mechanism, characterized in that: The method is used for thermally controlling the solar wing drive rotary mechanism according to any one of claims 1 to 4, comprising the following steps: S01, a plurality of temperature control points are arranged on the bottom plate (131), each heater (16) corresponds to one of the temperature control points, and the current temperature of each of the temperature control points is monitored in real time; S02, determining whether the temperature of each temperature control point is within a set range, if the temperature of each temperature control point is within the set range, executing step S03; otherwise, executing step S04; S03, determining whether the difference between the maximum and minimum current temperatures of the plurality of temperature control points is greater than a set difference; if so, controlling the power of the heater (16) corresponding to the temperature control point with the lowest current temperature to be increased by a first set value for a first set time, and then returning to execute step S01; if not, no operation; S04, adjusting the heating power of the heater (16) corresponding to the temperature control point whose temperature is not within the set range, for a second set time, and then returning to execute step S01, wherein the second set time is greater than the first set time.

7. The thermal control method of the solar wing drive rotary mechanism according to claim 6, characterized in that: The step S04 comprises: S041, determining whether the current temperature of the temperature control point whose temperature is not within the set range is greater than the minimum value of the set range; if not, controlling the power of the heater (16) corresponding to the temperature control point whose temperature is not within the set range to be increased by a second set value, and continuing for the second set time, returning to execute step S01, and the second set value is greater than the first set value; if yes, executing step S042; S042, controlling the power of the heater (16) corresponding to the temperature control point whose temperature is not within the set range to be reduced by the second set value, and after the second set time has passed, returning to execute step S01.

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